JPH09312518A - Dual reflection mirror antenna system - Google Patents

Abstract

PROBLEM TO BE SOLVED: To reduce deterioration in electric characteristics by providing supports with a shape to reduce its area of shutting a ray of the dual reflection mirror antenna system (equipment) and with an arrangement, as a 1st support with a strength withstanding a load in the case of use of the system in the space and a 2nd support with a strength withstanding a load in the case of transportation of the system into the space and discharging the 2nd support into the space. SOLUTION: A support 4 used to support a sub reflecting mirror 2 at a prescribed position is arranged with a shape having a smaller right receiving area for a spherical wave reflected from the sub reflecting mirror 2 or a plane wave reflected from the main reflecting mirror and is made up of a 1st support 4a with a strength withstanding a load in the case of use of the system in the spade and a 2nd support 4b with a strength withstanding a load in the case of transportation of the system into the space. The 2nd support 4b withstands vibration or the like caused in the case of launching a rocket. Furthermore, the system has a mechanism 6 which disconnects them from the system in the space.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a space double reflector antenna device which is launched by, for example, a rocket and is transported to outer space for use.

[0002]

2. Description of the Related Art Conventionally, as this type of device, there has been one as shown in FIG. This figure is the Institute of Electronics, Information and Communication Engineers,
Antenna Engineering Handbook, p. 300, 10 years of 1980
Shown by Ohmsha on March 30, 1 in the figure
Is a main reflecting mirror consisting of a paraboloid of revolution, 2 is a sub-reflecting mirror consisting of a rotating hyperboloid, 3 is a primary radiator consisting of a horn whose phase center is located at one focus of the sub-reflecting mirror 2, 4 is a sub-reflector Supports 5 for holding the mirror 2 are satellite structures. In the case of transmitting with the conventional Cassegrain antenna, the primary radiator 3
The radiated spherical wave is reflected by the sub-reflecting mirror 2, is converted into a spherical wave having the focus of the main reflecting mirror 1 as the center of curvature, propagates toward the main reflecting mirror 1, and is reflected by the main reflecting mirror 1. It is converted into a plane wave and is radiated in the mirror axis direction (z-axis direction in the drawing).

[0003]

Since the conventional double-reflecting mirror antenna device is constructed as described above, blocking, reflected waves, and diffracted waves are generated by the support holding the sub-reflecting mirror, so that the electrical performance is improved. Deteriorates. In the space antenna, the support that holds the sub-reflector is configured to withstand the vibrations and shocks at launch of the rocket,
The support is larger than the ground antenna. Therefore, there is a problem in that the effects of blocking by the support, reflected waves, and diffracted waves are further increased, and the electrical performance is greatly deteriorated, such as gain reduction, main beam shape change, and sidelobe level increase. It was

The present invention has been made to solve the above problems, and provides a double-reflecting mirror antenna device capable of reducing the deterioration of the electrical performance due to the support for holding the sub-reflecting mirror. With the goal.

[0005]

A multi-reflecting mirror antenna device according to claim 1 comprises a main reflecting mirror, a sub-reflecting mirror, a primary radiator, and a support for holding the sub-reflecting mirror. In the device, at least the support is installed in a shape and an arrangement in which the area for blocking the geometrical optical rays of the double reflector antenna device is reduced, and the load when the double reflector antenna device is used in outer space. A first support having sufficient strength to withstand the above, and a second support having sufficient strength to withstand the load of the double-reflecting mirror antenna device when it is transported to outer space. When the support is used in the space, the double-reflecting mirror antenna device is provided with a disconnecting mechanism that removes it from the radio wave path of the double-reflecting mirror antenna device.

The double reflector antenna device according to claim 2 is the double reflector antenna device according to claim 1, wherein the double reflector antenna device is installed independently of the second support or together with the second support. Deployed when using the multi-reflecting mirror antenna device in, to deploy a shielding member for shielding the inconvenient sunlight irradiating the main reflecting mirror, the shielding member,
And a shield member deploying mechanism that is driven and installed at a position that shields inconvenient sunlight irradiating the main reflector outside the radio wave path of the multi-reflector antenna device.

Further, a double-reflecting mirror antenna device according to a third aspect of the present invention is a double-reflecting mirror antenna device comprising a main reflecting mirror, a sub-reflecting mirror, a primary radiator, and a support for holding the sub-reflecting mirror. If the support is installed at least in a shape and arrangement in which the area for blocking the geometrical optical rays of the double-reflecting mirror antenna device is reduced, and if it can withstand the load when the double-reflecting mirror antenna device is used in outer space. The first support having sufficient strength, and the strength sufficient to withstand the load of the double-reflecting mirror antenna device when it is transported to outer space, provided between the main reflecting mirror and the sub-reflecting mirror. And a second support composed of a plurality of mirror surface members having a curved surface shape with a mirror surface constant different from that of the above-mentioned sub-mirror member when the double reflector antenna device is used in outer space. Supports connection to reflector Released to those having a mirror member deployment mechanism to deploy at a position for reflecting the radio waves spillover of the outer periphery of the opening of the main reflector.

Further, a double-reflection mirror antenna device according to a fourth aspect of the present invention is a double-reflection mirror antenna device comprising a main reflection mirror, a sub-reflection mirror, a primary radiator, and a support for holding the sub-reflection mirror. If the support is installed at least in a shape and arrangement in which the area for blocking the geometrical optical rays of the double-reflecting mirror antenna device is reduced, and if it can withstand the load when the double-reflecting mirror antenna device is used in outer space. The first support having sufficient strength, and the strength sufficient to withstand the load of the double-reflecting mirror antenna device when it is transported to outer space, provided between the main reflecting mirror and the sub-reflecting mirror. And a second support composed of a plurality of mirror surface members having a curved surface shape with the same mirror surface constant, and the plurality of mirror surface members are used when the double reflector antenna device is used in outer space. Supports connection to sub-reflector Released to those having a mirror member deployment mechanism to deploy at a position for reflecting the radio waves spillover of the outer periphery of the opening of the main reflector.

Further, a double-reflecting mirror antenna device according to a fifth aspect is the double-reflecting mirror antenna device according to the third or fourth aspect, in which the opening shape of the main reflecting mirror has a linear portion in part or all thereof. Shaped, when the above-mentioned double-reflecting mirror antenna device is used in outer space, the plurality of developed mirror surface members are electrically continuously connected to the main reflecting mirror through the straight line portion of the main reflecting mirror. Is.

[0012] According to a sixth aspect of the present invention, there is provided a double reflector antenna device according to the third, fourth, or fifth aspect, wherein the plurality of mirror surface members are outer space of an opening of the main reflector in outer space. And a metal mesh that is stretched between the plurality of mirror surface members and that reflects a spillover electric wave when deployed.

According to a seventh aspect of the present invention, there is provided a double-reflecting mirror antenna device according to the fifth aspect, wherein the main reflecting mirror and the plurality of mirror surface members are formed in the same shape. When the outer periphery of the opening of the main reflecting mirror is developed in outer space, the opening obtained by the main reflecting mirror and the plurality of mirror surface members has a circular or elliptical shape.

[0012] According to an eighth aspect of the present invention, there is provided a double reflector antenna device according to any one of the first to seventh aspects, wherein the first support is the double reflector antenna device. The sub-reflecting mirror is held at a position close to the main reflecting mirror during transportation to outer space, and the sub-reflecting mirror is fixed to the main reflecting mirror when the multi-reflecting mirror antenna device is used in space. It is provided with a sub-reflecting mirror drive mechanism for driving and holding the sub-reflecting mirror.

[0013]

BEST MODE FOR CARRYING OUT THE INVENTION

Embodiment 1. 1 is a configuration diagram showing a first embodiment of the present invention. FIG. 1A shows a rocket launched for transportation to outer space, and FIG. 1B shows an antenna used in outer space. . Reference numerals 1, 2, 3, and 5 correspond to the conventional device shown in FIG. 10, and operate similarly to the conventional device. In the figure, a case of transmitting with a Cassegrain antenna, which is a type of double reflector antenna, will be described as an example. 4 is a sub-reflecting mirror 2
Is a support body for holding in a predetermined position, and is installed in a shape and arrangement having a small area where a geometrical-optical beam of spherical waves reflected by the sub-reflecting mirror 2 or plane waves reflected by the main reflecting mirror 1 is irradiated. In addition, the pillar 4a, which is the first support having a strength sufficient to withstand the load of the double-reflecting mirror antenna device when it is used in outer space, and the shape having a large area to which the geometrical optical beam is applied are provided. And a member 4b, which is a second support having a strength that can withstand the load when the double reflector antenna device is transported to outer space, and by providing the member 4b as shown in FIG. Obtain strength to withstand vibrations and impacts at launch. 6 is a member 4b
Is a member detaching mechanism for detaching from the double-reflecting mirror antenna device in outer space. As shown in FIG. 7B, when the antenna is used in outer space, the member 4b is moved to a region where geometrical optical rays are not irradiated. Let Prop 4a
As shown in FIG. 2B, since the sub-reflecting mirror 2 may be held in a weightless state, the sub-reflecting mirror 2 can have a sufficiently small shape. Therefore, when the antenna is used in outer space, only the columns 4a are present in the region where the geometrical optical rays are irradiated, so that the influence of blocking by the support 4, reflected waves, and diffracted waves is small. It is possible to suppress deterioration of electrical performance.

Embodiment 2 FIG. 2A and 2B are configuration diagrams showing Embodiment 2 of the present invention. FIG. 2A shows a rocket launched, and FIG. 2B shows an antenna used in outer space.
Reference numerals 1, 2, 3, and 5 correspond to the conventional device shown in FIG. 10, and operate similarly to the conventional device. The supporting body 4 in the figure is configured by changing the mounting position of the supporting body 4 of FIG. 1 with respect to the main reflecting mirror 1 and is configured by three pieces, and the same effect as that of the first embodiment of the invention is obtained.

Embodiment 3 3A and 3B are configuration diagrams showing Embodiment 3 of the present invention. FIG. 3A shows a rocket launched, and FIG. 3B shows an antenna used in outer space.
In the figure, reference numerals 1, 2, 3, 5 correspond to the conventional device shown in FIG. 10, and operate similarly to the conventional device. Reference numeral 4 denotes a support for holding the sub-reflecting mirror 2 at a predetermined position, which has an area for irradiating a geometrical optical ray by a spherical wave reflected by the sub-reflecting mirror 2 or a plane wave reflected by the main reflecting mirror 1. A pillar 4a having a small shape and a member 4 having a shape having a large area irradiated with the geometrical optical ray.
b and a shielding member 4c. By providing the member 4b as shown in FIG. 4 (a), it is possible to obtain a strength capable of withstanding vibrations and impacts when the rocket is launched. In addition,
The above example shows the case where the member 4b which is the second support and the shield member 4c are connected and installed together. 6
Is a member separating mechanism for separating the member 4b from the double-reflecting mirror antenna device in outer space, 7 is a shield plate for blocking direct light from the sun behind the main reflecting mirror 1 to the main reflecting mirror 1, and 8 is a shield member 4c is a shield member deploying mechanism that is installed by moving 4c between the main reflecting mirror 1 and the sun. As shown in FIG. 2B, when the antenna is used in outer space, the member 4b is moved to a region where geometrical optical rays are not irradiated, and the shielding member expansion mechanism 8 moves the shielding member 4c between the main reflecting mirror 1 and the sun. It is driven and deployed in between, and when the antenna is used in outer space, it shields direct light from the sun to the main reflecting mirror 1 together with the shield plate 7. Therefore, the shielding member 4c and the shielding plate 7 shield the sun and suppress the thermal deformation of the main reflecting mirror 1 due to the temperature rise, so that the deterioration of the electrical performance can be suppressed. Further, since the support column 4a only needs to hold the sub-reflecting mirror 2 in a weightless state, it can be configured to have a sufficiently small shape, and the influence of blocking by the support body 4, reflected waves, and diffracted waves can be reduced, thereby deteriorating the electrical performance. Can be suppressed.

Embodiment 4 4A and 4B are configuration diagrams showing Embodiment 4 of the present invention. FIG. 4A shows a rocket launched, and FIG. 4B shows an antenna used in outer space.
In the figure, reference numerals 1, 2, 3 and 5 correspond to the conventional device shown in FIG. 10, and operate in the same manner as the conventional device. Four
Is a support for holding the sub-reflecting mirror 2 in a predetermined position,
A pillar 4a having a shape with a small area to which a geometrical-optical ray of a spherical wave reflected by the sub-reflecting mirror 2 or a plane wave reflected by the main-reflecting mirror 1 is irradiated, and this geometrical-optical ray is irradiated. A mirror member 4 having a large area and a curved surface having a mirror constant different from that of the main reflecting mirror 1.
The mirror surface member 4d provides sufficient strength to withstand vibrations and impacts when the rocket is launched. Reference numeral 9 denotes a mirror surface member deploying mechanism that drives and holds the mirror surface member 4d in the outer space of the outer periphery of the opening of the main reflecting mirror 1 in a space where geometrical optical rays exist. As shown in FIG. 2B, when the antenna is used in outer space, a part of the spherical wave reflected by the sub-reflecting mirror 2 is reflected by the mirror surface member 4d to reduce the spillover. Is the main reflector 1
Since it has a curved surface shape with a mirror surface constant different from
The reflection at d is radiated in a direction other than the main beam direction and is added in a phase opposite to the radiation pattern by the main reflecting mirror 1 to reduce the side lobe level. Further, since the support column 4a can be configured to have a sufficiently small shape, it is possible to reduce the influence of blocking by the support body 4, reflected waves, and diffracted waves, and suppress deterioration of electrical performance.

Embodiment 5 5A and 5B are configuration diagrams showing a fifth embodiment of the present invention. FIG. 5A shows a rocket launched, and FIG. 5B shows an antenna used in outer space.
In the figure, reference numerals 1, 2, 3 and 5 correspond to the conventional device shown in FIG. 10, and operate in the same manner as the conventional device. Four
Is a support for holding the sub-reflecting mirror 2 in a predetermined position,
A pillar 4a having a shape with a small area to which a geometrical-optical ray of a spherical wave reflected by the sub-reflecting mirror 2 or a plane wave reflected by the main-reflecting mirror 1 is irradiated, and this geometrical-optical ray is irradiated. A mirror surface member 4e having a large area and a curved surface having the same mirror surface constant as the main reflecting mirror 1.
The mirror surface member 4e provides sufficient strength to withstand vibrations and impacts when the rocket is launched. Reference numeral 10 denotes a mirror surface member deploying mechanism that drives and holds the mirror surface member 4e in a space where geometrical optical rays on the outer circumference of the opening of the main reflecting mirror 1 exist in the space. The mirror surface member 4e has the same mirror surface as the main reflecting mirror 1. Since it has a constant, the spherical wave reflected from the sub-reflecting mirror 2 can be reflected by the mirror surface member 4e to reduce spillover, and can be radiated as a plane wave in the mirror axis direction to increase the gain. In addition, since the support column 4a can be configured with a sufficiently small shape, blocking by the support body 4,
The influence of reflected waves and diffracted waves can be reduced, and deterioration of electrical performance can be suppressed.

Embodiment 6 FIG. 6A and 6B are configuration diagrams showing a sixth embodiment of the present invention. FIG. 6A shows a rocket launched, and FIG. 6B shows an antenna used in outer space.
Reference numerals 2 and 3 are equivalent to the conventional device shown in FIG. 10, and operate similarly to the conventional device. Further, 4a and 10 are the same as those of the embodiment of the invention shown in FIG. 4f is
A part or all of the opening shape is a mirror surface member that is electrically and continuously connected to the main reflecting mirror 1 that is a straight line, a polygonal line, or a polygon, and the main reflecting mirror 1 and the mirror surface member 4f are continuously connected. As a result, the deterioration of the aperture distribution due to the disturbance of the current distribution in the vicinity of the aperture edge can be suppressed, and since the mirror surface member 4f has the same mirror surface constant as the main reflecting mirror 1, the spherical wave reflected by the sub reflecting mirror 2 is Mirror surface member 4f
It is possible to reduce the spillover by being reflected by, and radiate as a plane wave in the direction of the mirror axis to increase the gain.
Further, since the support column 4a can be configured to have a sufficiently small shape, it is possible to reduce the influence of blocking by the support body 4, reflected waves, and diffracted waves, and suppress deterioration of electrical performance.

Embodiment 7. 7A and 7B are configuration diagrams showing a seventh embodiment of the present invention. FIG. 7A shows a rocket launched, and FIG. 7B shows an antenna used in outer space.
Reference numerals 2 and 3 are equivalent to the conventional device shown in FIG. 10, and operate similarly to the conventional device. Also, 1, 4a, 4f, 1
0 is the same as the embodiment of the invention shown in FIG. Reference numeral 11 denotes a metal mesh that is electrically connected to the mirror surface member 4f in the outer space and is stretched in a space that spills over to reflect radio waves. Reference numeral 12 denotes a metal mesh joint portion that connects the mirror surface member 4f and the metal mesh 11. As shown in FIG. 2B, when the antenna is used in outer space, the metal mesh 11 opens with the expansion of the mirror member 4f, and the antenna opening can be made larger, resulting in higher efficiency, blocking by the support 4 and reflected waves. , And spillover can be reduced while suppressing the influence of diffracted waves, and deterioration of electrical performance can be suppressed.

Embodiment 8. 8A and 8B are configuration diagrams showing an eighth embodiment of the present invention. FIG. 8A shows a rocket launched, and FIG. 8B shows an antenna used in outer space.
In the eighth embodiment of the present invention, the shapes of the main reflecting mirror and the plurality of mirror surface members are changed to the above-mentioned main surfaces when the plurality of mirror surface members are deployed on the outer circumference of the opening of the main reflecting mirror in outer space. An example is shown in which the opening obtained by the reflecting mirror and the plurality of mirror surface members is formed to have an elliptical shape. In the drawing, 13 is a main reflecting mirror having an aperture shape A _m , and 14
Is a sub-reflecting mirror with an aperture shape A _s , 15 is a primary radiator with an aperture shape A _h , 4 is a support for holding the sub-reflecting mirror 14 with an aperture shape A _s , and 4 g is against rocket launching vibrations and impacts. holding the secondary reflecting mirror 14 of the opening shape a _s, at the time the antenna used in space to reflect the spherical wave reflected from the auxiliary reflecting mirror 14 of the opening shape a _s is converted into a plane wave, the opening shape a _m
Mirror member opening shape A for emitting the main beam direction of the main reflecting mirror 13, and 10 drives the mirror member 4g of the opening shape A fixed mirror position determined by the mirror constants of the main reflecting mirror 13 of the opening shape A _m It is a mirror surface member deployment mechanism. As shown in Fig. 2 (b), when using the antenna in outer space, the aperture shape A _s
The geometric optical beam reflected by the secondary reflecting mirror 14 is converted into a plane wave propagating in the same direction is reflected by the mirror member 4g of the main reflecting mirror 13 or the opening shape A of all opening shape A _m radiation. When using the antenna in outer space,
Since the antenna aperture can be made larger with a simple configuration, the efficiency is increased, and spillover can be reduced and electrical performance can be improved while the influence of blocking by the support 4, reflected waves, and diffracted waves is reduced.

Ninth Embodiment 9A and 9B are configuration diagrams showing Embodiment 9 of the present invention. FIG. 9A shows a rocket launched, and FIG. 9B shows an antenna used in outer space.
Reference numerals 1, 2, 3, and 5 correspond to the conventional device shown in FIG. 10, and operate similarly to the conventional device. Reference numeral 4 denotes a support for holding the sub-reflecting mirror 2 at a predetermined position, which has an area for irradiating a geometrical optical ray by a spherical wave reflected by the sub-reflecting mirror 2 or a plane wave reflected by the main reflecting mirror 1. A first support having a sub-reflecting mirror driving mechanism 4h having a small shape and driving the sub-reflecting mirror 2 in the mirror axis direction of the main reflecting mirror 1;
The second support is composed of a member 4b having a shape having a large area irradiated with the geometrical optical ray. By providing the member 4b as shown in FIG. 7A, it is possible to obtain strength enough to withstand vibration and impact at the time of launching the rocket, and further, since the sub-reflector drive mechanism 4h is provided, it is a sub-device at the time of launching the rocket. Since the reflecting mirror 2 can be arranged near the main reflecting mirror 1, the member 4b can be made compact. Reference numeral 6 denotes a member separating mechanism for separating the member 4b from the double-reflecting mirror antenna device in outer space. As shown in FIG. 6B, when the antenna is used in outer space, the member 4b is irradiated with geometrical optical rays. Then, the sub-reflecting mirror drive mechanism 4h moves and sets the sub-reflecting mirror 2 to a predetermined position. Therefore, when the antenna is used in outer space, only the pillar 4a having the sub-reflecting mirror drive mechanism 4h exists in the area irradiated with the geometrical optical beam, so that the blocking by the support 4 and the reflected wave. , And the influence of diffracted waves can be reduced, and deterioration of electrical performance can be suppressed.

In the embodiment of the present invention described above, the case of transmission is described as an example, but it acts reversibly also in the case of reception, and is equally effective for the purpose of the present invention. is there. Further, although the conical horn is used as the primary radiator, a corrugated horn, a multi-mode horn, or a horn having another shape has the same effect as that of the embodiment of the invention. In addition, although the case of the Cassegrain antenna is shown as the double reflector antenna device, even in the case of the Gregorian antenna and other types of radiation systems,
It has the same effects as those of the respective embodiments of the invention.

[0023]

Since the present invention is configured as described above, the following effects can be obtained.

According to the first aspect of the present invention, the support for holding the sub-reflecting mirror is installed at least in a shape and arrangement in which the area of the multi-reflecting mirror antenna device that blocks the geometrical optical rays is reduced, and the double-reflecting mirror is installed. A first support that is strong enough to withstand the load of the mirror antenna device when it is used in outer space, and a second support that is strong enough to withstand the load of the double-reflection mirror antenna device when it is transported to outer space. Divided into at least the above second
When the above-mentioned double-reflecting mirror antenna device is used in outer space, since a detachment mechanism is provided to remove the radio wave of the above-mentioned double-reflecting mirror antenna device out of the path, the secondary reflection of the double-reflecting mirror antenna device used in outer space The influence of blocking, reflected waves, and diffracted waves by the support of the mirror can be reduced, and deterioration of electrical performance can be suppressed.

Further, according to the invention of claim 2, in the double-reflecting mirror antenna device used in outer space, the shielding member for shielding inconvenient sunlight irradiating the main reflecting mirror and the shielding member are developed, and Since it is equipped with a shield member expansion mechanism that is installed by driving it to a position that shields the inconvenient sunlight irradiating the main reflector outside the radio wave path of the double reflector antenna device, thermal deformation due to temperature rise of the main reflector Can be suppressed, and blocking by the shielding member, reflected waves,
Also, the influence of diffracted waves can be reduced, and deterioration of electrical performance can be suppressed.

According to the third aspect of the present invention, when the double reflector antenna device is used in outer space, the second support is made up of a plurality of mirror surface members having a curved surface shape having a mirror surface constant different from that of the main reflecting mirror. Since the mirror surface member developing mechanism deploys the plurality of mirror surface members to a position on the outer periphery of the opening of the main reflecting mirror for reflecting spillover electric waves, the reflection on the mirror surface member is directed in a direction other than the main beam direction. The side lobe level is lowered by being emitted and added in a phase opposite to the radiation pattern of the main reflecting mirror.

Further, according to the invention of claim 4, when the double reflecting mirror antenna device is used in outer space, the second support has a plurality of mirror surface members having a curved surface shape having the same mirror surface constant as the main reflecting mirror. Since the mirror surface member developing mechanism deploys the plurality of mirror surface members to a position for reflecting spillover electric waves on the outer periphery of the opening of the main reflecting mirror, the reflection on the mirror surface member is radiated in the main beam direction. , Spillover can be reduced and gain can be increased.

According to the invention of claim 5, the second support is composed of a plurality of mirror surface members having a curved surface shape having the same mirror surface constant as the main reflecting mirror, and the opening shape of the main reflecting mirror is When a part of or the whole of which has a straight line portion, the plurality of mirror surface members that have been deployed when the above-described double reflector antenna device is used in outer space, the main reflection through the straight line portion of the main reflecting mirror. Since the mirror surface member deploying mechanism electrically connected to the mirror deploys the plurality of mirror surface members to the position on the outer periphery of the opening of the main reflecting mirror for reflecting the spillover electric wave, in the vicinity of the opening edge of the main reflecting mirror. The deterioration of the aperture distribution due to the disturbance of the current distribution can be suppressed, and the reflection on the mirror surface member is radiated in the main beam direction,
Spillover can be reduced and gain can be increased.

According to the sixth aspect of the present invention, when a plurality of mirror surface members are deployed on the outer periphery of the opening of the main reflecting mirror in space, the radio waves are expanded between the plurality of mirror surface members and spill over. Since it has a metal mesh that reflects
When using a double reflector antenna device in outer space, the antenna aperture can be made larger than the main reflector to achieve high efficiency, and the spillover radio wave can be reflected to reduce spillover.

Further, according to the invention of claim 7, the shapes of the main reflecting mirror and the plurality of mirror surface members are set such that when the plurality of mirror surface members are developed in outer space around the outer periphery of the opening of the main reflecting mirror. Since the opening obtained by the main reflecting mirror and the plurality of mirror surface members is formed to have a circular or elliptical shape, when using the double reflecting mirror antenna device in outer space, the antenna opening can be formed with a simple structure. Since it can be made larger, high efficiency can be achieved and spillover can be reduced by reflecting radio waves that spillover.

According to the invention of claim 8, the first support holds the sub-reflector at a position close to the main reflector when the multi-reflector antenna device is transported to outer space. Since the sub-reflector antenna device is equipped with a sub-reflector drive mechanism that drives and holds the sub-reflector at a predetermined position relative to the main reflector when the device is used in outer space, the second support is formed in a small size. Therefore, the storage space for the antenna can be reduced when the double reflector antenna device is transported to outer space.

[Brief description of drawings]

FIG. 1 is a configuration diagram showing a double reflector antenna device according to a first embodiment of the present invention.

FIG. 2 is a configuration diagram showing a double reflector antenna device according to a second embodiment of the present invention.

FIG. 3 is a configuration diagram showing a double reflector antenna device according to a third embodiment of the present invention.

FIG. 4 is a configuration diagram showing a double reflector antenna device according to a fourth embodiment of the present invention.

FIG. 5 is a configuration diagram showing a double reflector antenna device according to a fifth embodiment of the present invention.

FIG. 6 is a configuration diagram showing a double reflector antenna device according to a sixth embodiment of the present invention.

FIG. 7 is a configuration diagram showing a double reflector antenna device according to a seventh embodiment of the present invention.

FIG. 8 is a configuration diagram showing a double reflector antenna device according to an eighth embodiment of the present invention.

FIG. 9 is a configuration diagram showing a double reflector antenna device according to a ninth embodiment of the present invention.

FIG. 10 is a configuration diagram showing a conventional example.

[Explanation of symbols]

DESCRIPTION OF SYMBOLS 1 main reflecting mirror, 2 sub-reflecting mirror, 3 primary radiator, 4 support, 4a support, 4b member, 4c shielding member, 4
d, 4e, 4f Mirror surface member, 4g Mirror surface member with aperture shape A, 4h Sub-reflecting mirror drive mechanism, 5 Satellite structure, 6 member separating mechanism, 7 Shield plate, 8 Shield member deploying mechanism, 9, 10 Mirror member deploying mechanism, 11 metal mesh, 12 metal mesh junction, 13 a main reflector opening shape a _m, 14 subreflector opening shape a _s, a primary radiator 15 opening shape a _h.

─────────────────────────────────────────────────── ─── Continuation of the front page (51) Int.Cl. ⁶ Identification code Internal reference number FI Technical indication H01Q 19/19 H01Q 19/19 // H01Q 13/02 13/02

Claims (8)

[Claims] 1. A multi-reflecting mirror antenna device comprising a main reflecting mirror, a sub-reflecting mirror, a primary radiator, and a support for holding the sub-reflecting mirror, wherein at least the support is provided in the multi-reflecting mirror antenna device. The first support, which is installed in such a shape and arrangement that the area for intercepting the geometrical optical rays is reduced, and has sufficient strength to withstand the load of the above-mentioned double-reflecting mirror antenna device when used in outer space, It is configured by being divided into a second supporting body having a strength capable of withstanding a load when the double reflecting mirror antenna device is transported to outer space, and at least the second supporting body is used in the outer space when the double reflecting mirror antenna device is used. A multi-reflecting mirror antenna device comprising a disconnecting mechanism for removing the radio wave from the multi-reflecting mirror antenna device to the outside of the radio wave path. 2. The multi-reflecting mirror antenna device according to claim 1, wherein the multi-reflecting mirror antenna device is installed independently of the second support or together with the second support, and is deployed when the multi-reflection mirror antenna device is used in outer space. The shielding member for shielding the undesired sunlight irradiating the main reflecting mirror and the shielding member are developed, and the undesired sunlight irradiating the main reflecting mirror outside the radio wave path of the double reflector antenna device is A multi-reflecting mirror antenna device comprising: a shield member deploying mechanism that is driven and installed at a shield position. 3. A multi-reflecting mirror antenna device comprising a main reflecting mirror, a sub-reflecting mirror, a primary radiator, and a support for holding the sub-reflecting mirror, wherein at least the support is provided in the multi-reflecting mirror antenna device. The first support, which is installed in such a shape and arrangement that the area for intercepting the geometrical optical rays is reduced, and has sufficient strength to withstand the load of the above-mentioned double-reflecting mirror antenna device when used in outer space, A plurality of curved surfaces having a mirror constant different from that of the main reflecting mirror, which is provided between the main reflecting mirror and the sub-reflecting mirror and has a strength that can withstand a load when the double reflecting mirror antenna device is transported to outer space. And a second support composed of a mirror surface member, and when the double reflection mirror antenna device is used in outer space, the support for connecting the plurality of mirror surface members to the sub-reflecting mirror is released, and The spin around the opening of the main reflector A multi-reflecting mirror antenna device comprising a mirror surface member deploying mechanism for deploying to a position for reflecting a radio wave that overruns. 4. A multi-reflecting mirror antenna device comprising a main reflecting mirror, a sub-reflecting mirror, a primary radiator, and a support for holding the sub-reflecting mirror, wherein at least the support is provided in the multi-reflecting mirror antenna device. The first support, which is installed in such a shape and arrangement that the area for intercepting the geometrical optical rays is reduced, and has sufficient strength to withstand the load of the above-mentioned double-reflecting mirror antenna device when used in outer space, A plurality of curved surfaces having the same mirror surface constant as the main reflecting mirror, which are provided between the main reflecting mirror and the sub-reflecting mirror and have a strength to withstand the load of the double-reflecting mirror antenna device when transported to outer space. And a second support made up of a single mirror surface member. When the double reflector mirror antenna device is used in outer space, the plurality of mirror surface members are disconnected from the sub-reflecting mirror. The spin around the aperture of the main reflector is A multi-reflecting mirror antenna device comprising a mirror surface member deploying mechanism for deploying to a position for reflecting a radio wave that overruns. 5. The double-reflecting mirror antenna device according to claim 3 or 4, wherein the opening of the main reflecting mirror has a linear part in part or in whole, and the double-reflecting mirror antenna in outer space. A multi-reflecting mirror antenna device, characterized in that, when the device is used, the plurality of developed mirror surface members are electrically continuously connected to the main reflecting mirror through the straight line portion of the main reflecting mirror. 6. The multi-reflecting mirror antenna device according to claim 3, 4 or 5, wherein when the plurality of mirror surface members are deployed on the outer periphery of the opening of the main reflecting mirror in space, the plurality of mirror surface members are provided. A multi-reflecting mirror antenna device comprising a metal mesh that is stretched between members and that reflects a spillover electric wave. 7. The multi-reflecting mirror antenna device according to claim 5, wherein the main reflecting mirror and the plurality of mirror surface members are shaped such that the plurality of mirror surface members are outer space of an opening of the main reflecting mirror in outer space. A multi-reflecting mirror antenna device, characterized in that an opening obtained by the main reflecting mirror and the plurality of mirror-finished members has a circular or elliptical shape when expanded. 8. The double-reflecting mirror antenna device according to claim 1, wherein the first support member transports the double-reflecting mirror antenna device to outer space. Is held at a position close to the main reflecting mirror, and the sub-reflecting mirror is driven and held at a predetermined position with respect to the main reflecting mirror when the double reflecting mirror antenna device is used in space. A double-reflecting mirror antenna device comprising a driving mechanism.